Gas turbine combustor exit duct and hp vane interface
US8166767B2 · kind B2 · utility
8Cited by
25References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 15, 2010 |
| Grant date | May 1, 2012 |
| Priority date | — |
| Expiry date | Oct 15, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.